Turbine, in particular for an exhaust gas turbocharger, and exhaust gas turbocharger

ABSTRACT

An exhaust gas turbocharger, comprising: a turbine rotor rotatably mounted in a housing, which is associated with at least one guide apparatus forming a radial inlet channel, wherein the guide apparatus includes at least one of a guide vane bearing ring, a plurality of guide vanes radially surrounding the turbine rotor and located in the inlet channel and a guide vane cover ring. The inlet channel is axially delimited by the guide vane bearing ring and the guide vane cover ring wherein the guide vane bearing ring and the guide vane cover ring are moveably mounted at least one of axially and radially relative to each other and to the housing. The guide apparatus is subjected to at least one of an axial and radial preload, wherein a line of axial preload flux runs through the guide apparatus substantially parallel to the rotational axis of the turbine rotor.

The invention relates to a turbine, in particular for an exhaust gasturbocharger with a turbine rotor rotatably mounted in a housing, whichis associated with at least one guide apparatus forming a radial inletchannel for a medium driving the turbine rotor.

Furthermore, the invention relates to an exhaust gas turbocharger, inparticular for a motor vehicle having a turbine and a compressor whichare operationally connected with each other mechanically.

PRIOR ART

Turbines, in particular in motor vehicle construction, are known fromthe prior art in connection with gas turbochargers having a turbinerotor rotatably mounted in a housing, which is associated with a leastone guide apparatus forming a radial inlet channel for a medium drivingthe turbine rotor. In motor vehicle construction turbochargers are usedto increase the power and the rotational moment of a combustion engine.The turbine more specifically the turbine rotor of the turbine of suchan exhaust gas turbocharger is driven by an exhaust gas flow of thecombustion engine and in turn drives a compressor which in turncompresses and drives drawn-in fresh air into the cylinders of thecombustion engine. By compressing the fresh air the fresh air componentintroduced in the cylinders of the combustion engine is increased andthe power and rotational moment increase achieved as a result. Since theturbine is driven by the exhaust gas of the combustion engine noadditional units for increasing the charging volume of the cylinders arenecessary. In the meantime, turbines are also used which have aso-called variable turbine geometry (VTG). Turbines with variableturbine geometry are based on the mode of operation of the Francisturbine and serve to better or optimally adjust/adapt the power outputand the response characteristics of the turbine or the exhaust gasturbocharger to different points of operation. To achieve this, aturbine with variable turbine geometry comprises a guide apparatusassigned to the turbine rotor and which forms a radial inlet channel forthe medium (in this case the exhaust gas of the combustion engine)driving the turbine rotor. In the inlet channel formed by the guideapparatus adjustable guide vanes are arranged which radially surroundthe turbine rotor. These guide vanes can be adjusted with respect totheir vane angle to change the flow cross section of the inlet channel.Usually, the guide vanes are distributed evenly or at equal angles overthe circumference of the turbine rotor and, spaced from this, on a guidevane bearing ring of the guide apparatus. The vane angle of the guidevanes for example is set in such a manner that with a low throughput ofthe medium driving the turbine rotor and with simultaneously high powerrequirement the flow cross section in the inlet channel is reduced sothat the medium is directed onto the turbine vanes in an acceleratedmanner, as a result of which the rotational speed of the turbine andthus the power of the compressor or the exhaust gas turbocharger isincreased. Conversely, with a high throughput of the medium and a lowpower requirement, the flow velocity of the medium can be reducedthrough a large flow cross section, as a result of which the power ofthe turbine and thus that of the exhaust gas turbocharger is reduced.

From the European Patent Publication EP 0160460 B1 a turbine asdescribed above is known, wherein the vane bearing ring is mountedaxially displaceably and, together with a housing section of the housingof the turbine, axially delimits the inlet channel.

DISCLOSURE OF THE INVENTION

The invention provides for a turbine with a turbine rotor rotatablymounted in a housing, which is associated with at least one guideapparatus forming a radial inlet channel for a medium driving theturbine rotor, wherein the guide apparatus comprises a guide vanebearing ring as well as a guide vane cover ring having a plurality ofguide vanes radially surrounding the turbine rotor and located in theinlet channel, and wherein the inlet channel is axially delimited by theguide vane bearing ring and the guide vane cover ring and the guideapparatus is mounted in the housing in an axially and/or radiallymoveable manner for material relaxation. The turbine according to theinvention thus comprises a guide apparatus which, in addition to theguide vane bearing ring comprises a guide vane cover ring, whichtogether with the guide vane bearing ring axially delimits the inletchannel for the medium driving the turbine rotor. The guide vane bearingring and the guide vane cover ring, as the name implies, are eachdesigned as a ring. Throughout the present application, guide vanebearing ring and guide vane cover ring each therefore does not mean abush or a bush-like element but a ring, comprising a simple crosssection preferably substantially rectangular in shape, whose radialextension is substantially equal or preferentially greater than itsaxial extension. Here, the guide vane cover ring is arranged parallel tothe guide vane bearing ring, wherein the distance between the guide vanebearing ring and the guide vane cover ring substantially corresponds tothe width or the axial extension of the guide vanes.

The guide vane cover ring has the advantage that stresses and/ordeformations of the housing of the turbine, which for example developbased on mechanical overloading and/or based on temperature-relatedstresses and/or deformations, do not impair the efficiency of the guideapparatus. The design of the guide apparatus by means of rings—guidevane bearing ring and guide vane cover ring—allows particularly simpleand cost-effective manufacture of the turbine.

In the mentioned prior art the guide vanes directly contact the housingof the turbine. Any deformation of the housing for the above mentionedreasons in this case will result in high friction values between theguide vanes and the housing in the event of an adjustment or a change ofthe vane angle of the guide vanes. It this stresses and deformations ofthe housings are sufficiently high, the guide vanes can no longer beadjusted or actuated. The variable turbine geometry is thus no longerfunctional. The guide vane cover ring thus substantially decouples thehousing of the turbine, so that the guide vane cover ring acts like abuffer for the stresses and deformations that occur in the housing. Inaddition to this, the guide vane cover ring is advantageouslymanufactured of a high-quality material. The guide vanes which inoperation contact the guide vane cover ring and move if required, easilylead to rapid corrosion, erosion and/or rapid wear of the contact pointson the guide vane cover ring. These corrosion point can be so pronouncedthat the guide vanes “seize” on the guide vane cover ring. This alsoprevents adjusting of the flow cross section of the inlet channel bymeans of the guide vanes. The advantageous guide vane cover ring which,as already mentioned, is manufactured of the high-quality material,prevents such corrosion because of its material properties. Obviously itwill also be conceivable to manufacture the entire turbine housing ofthe high-quality material, but this would result in extremely high costsand high manufacturing expenditure, which can be avoided through the useof the advantageously designed guide vane cover ring. According to theinvention, the entire guide apparatus consisting of the guide vanebearing ring, the guide vanes and the guide vane cover ring is nowmounted axially and/or radially moveable in the housing for materialrelaxation. The guide apparatus is not fixed to the housing for exampleby means of a screw connection. The guide apparatus mounted axiallyand/or radially moveable allows relative movement between itself and thehousing, as a result of which stresses both in the guide apparatus aswell as in the housing are reduced and because of this the lifespan ofthe guide apparatus or the turbine is increased. This allowstemperature-related expansion/extension of the individual components ofthe guide apparatus without stresses developing in the guide apparatus,particularly when hot exhaust gasses of a combustion engine are admittedto the turbine. In radial and/or axial extension of the guide apparatusplay is practically provided to the housing which is of such a size thatthe material of the guide apparatus and/or of the housing can expandeven under high (temperature) loading without “jamming” the guideapparatus in the housing. The mounting of the guide apparatus thusallows relaxation of the material through axial and/or radial(compensatory) movement.

According to a further development of the invention the guide apparatusis mounted axially moveable without preload. The guide apparatus nowlies in the housing in a “loose” or “floating” manner so that it canfreely move for material relaxation.

However, the guide apparatus is preferably subjected to an axial preloadand/or radial clamping which fix the guide apparatus axially and/orradially in the housing in such a manner that the guide apparatus ispressed against the housing and wobbling for example due to shocks orvibrations is thus prevented. Practically, the preload is selected suchthat it is significantly smaller than the stresses that occur in theguide apparatus, in particular due to temperature. The guide apparatusis thus mounted in the housing in a floating manner (without preload) orwith at least a (small) preload.

Advantageously the guide vane bearing ring and the guide vane cover ringeach lie in an axial depression of the housing. The axial depression inthis case can for example be milled, turned or bored into the housing ina simple manner. Practically, the contour of the axial depressionsubstantially corresponds to that of the guide vane bearing ring or thatof the guide vane cover ring, so that these have the necessary play formaterial relaxation at their disposal.

According to a further development of the invention the housing isdesigned in multiple parts. This makes possible particularly simple andcost-effective assembly of the guide apparatus in the housing or in theaxial depressions of the housing. Practically, the guide apparatus isinitially placed axially in the axial depression of a housing part andthe other housing part subsequently pushed onto the (axial) free end ofthe guide apparatus.

Advantageously, the first housing part is a turbine housing. The turbinehousing substantially surrounds the turbine rotor of the turbine andpractically comprises a radial, more preferably ring-spiral shaped inletchannel which directs the medium towards the inlet channel of the guideapparatus and a central or axial outlet channel, which extends in theaxial extension of the turbine rotor.

Practically, the second housing part is a bearing housing. In thebearing housing a shaft, on which the turbine rotor is mounted in arotationally fixed manner, is rotatably mounted. Particularlypreferably, the shaft is mounted in the bearing housing by means of oneor a plurality of rolling bearings such as for example grooved ballbearings, tapered roller bearings etc. Slide bearing mounting of theshaft is also conceivable. The bearing housing axially follows theturbine housing.

Furthermore it is provided that the axial depression for the guide vanebearing ring is formed in the bearing housing and the axial depressionfor the guide vane cover ring in the turbine housing. In principle,reverse arrangement is also possible, wherein the guide vane bearingring lies in the axial depression in the turbine housing and the guidevane cover ring in the axial depression of the bearing housing.Preferred, however, is the first version, since in this case thenecessary mechanism for the displacement of the guide vanes for packagereasons (space) can be more easily arranged in the bearing housing thanin the turbine housing, which has to be designed particularlyflow-favourable for the medium driving the turbine rotor.

An advantageous further development of the invention provides that theturbine comprises at least one axial spring element for generating theaxial preload. As already mentioned above, the spring load, compared tothe temperature-related stresses of the guide apparatus, is selectedsmall. Here, it can be provided that merely an axial spring element isused, which presses the guide apparatus against one of the axialdepressions, or two or more axial spring elements can be provided whichare each arranged for example at an axial end of the guide apparatus.

Preferably, the axial spring element is arranged between the guide vanebearing ring and the housing, or the bearing housing, and/or between theguide vane cover ring and the housing, or the turbine housing. If theaxial spring element is arranged between the guide vane bearing ring andthe bearing housing, this has the advantage that the axial springelement is not severely heated since the bearing housing is relativelycool. The reason for this is that it does not come in contact with thehot exhaust gas or only to an extremely minor degree. Through thearrangement of the axial spring element of the bearing housing thelifespan of the spring is thus increased or guaranteed. If the axialspring element however is arranged (axially) between the guide vanecover ring and the turbine housing it is located on the hot side of theturbine. Because of this, the guide apparatus is pressed in thedirection of the cold side, that is against the bearing housing. Throughthe direct contact of the guide vane bearing ring with the bearinghousing the guide apparatus is “cooled” by the bearing housing.

Advantageously, the axial spring element is designed as helical spring,coil spring or disc spring. Wherein, in addition to the mentioned axialspring element types, the use of an O-ring, taper ring, barrel springring, B-ring, C-ring, a metal sealing ring or a sponge-like fabric isconceivable for example. The material of the axial spring element can beof a wide range of types such as for example metal or a compositematerial or ceramic. Particularly preferred, the disc spring issimultaneously designed as heat shield and/or as seal.

Furthermore, it is provide that the turbine comprises at least oneradial spring element for radiating the radial preload. This ispreferably arranged between the housing and the outer and/or innercircumference of the guide vane cover ring. Like the axial springelement the radial spring element has a spring force which relative tothe stresses developing in the guide apparatus, is small, so that theguide apparatus can radially expand freely so that its material remainslow-stressed or “relaxed”.

Particularly preferably, the radial spring element is designed as a wavyring. The wavy ring, also called bearing compensation ring, in this caseextends over the entire inner or outer circumference of the guide vanecover ring or the guide vane bearing ring. Obviously an open guide vanecover ring or guide vane bearing ring is also conceivable.

In an advantageous further development of the invention the turbinecomprises at least one radial-axial spring element for generating theaxial and the radial preload. Instead of an axial spring element and aradial spring element it is thus provided to use a single radial-axialspring element which simultaneously generates the axial and radialpreload, applying it to the guide apparatus. The radial-axial springelement can for example be formed of a pleated ring with radial pleatswhich contacts the housing and the guide apparatus both axially as wellas radially.

Furthermore, it is provided in an advantageous further development ofthe invention that the guide vane bearing ring and the guide vane coverring are axially and/or radially displaceable relative to each other formaterial relaxation. Here, not only the entire guide apparatus ismoveably mounted in the housing, but the individual components/parts ofthe guide apparatus are also moveably mounted relative to one another.Wherein in the case of preload-free mounting of the guide apparatus theguide vane bearing ring and the guide vane cover ring are also loose,that is moveable, relative to each other without preload. If the guideapparatus is subjected to axial preload this obviously also has aneffect on the components of the guide apparatus so that the guide vanebearing ring is axially pressed against the guide vane bearing ring (orvice versa). The free moveability or the loose arrangement of the guideapparatus and that of the guide vane bearing ring to the guide vanecover ring results in that the play of the guide vanes between the guidevanes and the guide vane cover ring can be designed particularly small,as a result of which the (thermodynamic) efficiency of the turbine isimproved. The turbine thus designed with “floating” variable turbinegeometry makes possible minimal deformations and stresses. Through thefree moveability of the guide vane bearing ring and the guide vane coverring the friction between the guide vanes and the guide vane cover ringis reduced so that in this case corrosion formation, erosion and/or wearare also prevented.

Advantageously, at least one, preferably a plurality of axial spacers isprovided between the guide vane bearing ring and the guide vane coverring. These axial spacers secure a minimum spacing of the guide vanebearing ring from the guide vane cover ring which is defined by theaxial extension of the axial spacer. The size of the axial spacer ispractically selected in such a manner that between the guide vanes andthe guide vane cover ring and the guide vane bearing ring preferablysmall play is present and a preferably low friction is in effect whenadjusting the guide vanes.

Advantageously, the axial spacers are arranged or fixed on the guidevane bearing ring and/or the guide vane cover ring. Thus all of theaxial spacers can be arranged on the guide vane cover ring or on theguide vane bearing ring or for example alternately on the guide vanecover ring and the guide vane bearing ring. In addition to this isconceivable that the axial spacers are designed in two parts, whereinone part is arranged on the guide vane bearing ring and the other partopposite on the guide vane cover ring. Because of the geometry of thecomponents and the different temperature loading the guide vane coverring is not deformed as much as the guide vane bearing ring. For thisreason, the axial spacers are preferably arranged or fixed on the guidevane cover ring. Inclined positioning of the guide vane cover ring dueto temperature-related stresses is only minor so that the axial spacerschange their contact with the guide vane bearing ring only to a minordegree and thus the axial extension or the width of the inlet channeland thus also the play between the guide vanes and the guide vane coverring and the guide vane bearing ring is changed/influenced only to aminor degree.

Particularly preferably, the axial spacers are unitarily formed with aguide vane bearing ring or the guide vane cover ring. Practically, theaxial spacers are arranged distributed evenly or equiangularly orunevenly or non-equiangularly on the end face of the guide vane bearingring and/or the guide vane cover ring facing the inlet channel. If theaxial spacers are designed in two parts the two parts are eachpreferably designed unitarily with the guide vane bearing ring or theguide vane cover ring.

Furthermore, it is provided that the turbine comprises at least one pinconnection for positioning and/or aligning the guide apparatus, theguide vane bearing ring and/or the guide vane cover ring on the housing.Preferably the pin connection comprises at least one pin which isinserted in a pin reception of the guide apparatus or one of itscomponents and/or the housing. By using one or a plurality of pinconnections the assembly of the turbine remains simple andcost-effective.

Practically, at least one pin reception is designed as elongated hole sothat relocating or moving of the guide apparatus, the guide vane bearingring or the guide vane cover ring relative to the pin inserted in thepin reception is possible.

Preferably, the elongated hole is orientated radially or axially in itslongitudinal extension. If the elongated hole is orientated radially,radial movement of the pin engaging in the elongated hole or anextension of the component comprising the pin is possible withoutgenerating stress. If the elongated hole in its longitudinal extensionis orientated axially, that is parallel to the rotational axis of theturbine rotor, corresponding expansion of the material due to risingtemperatures is possible in axial direction without stresses beinggenerated.

Advantageously, the pin is orientated axially and/or radially. In bothcases it acts as positioning device or anti-rotation safety. If it isorientated axially, it allows axial movement of the guide apparatus orits components for material relaxation. If it is orientated radially itcorrespondingly allows radial movement/expansion for materialrelaxation. Obviously in both cases it is presumed that the pin in itslongitudinal extension is moveably mounted with adequate play.

Furthermore, it is provided that at least one pin of a pin connection isformed by one of the axial spacers. Here it is provided that the axialspacer protrudes through the guide vane bearing ring or the guide vanecover ring and stands away on the face end located opposite the inletchannel from the corresponding ring and engages in a pin reception ofthe housing. Alternatively to this, the pin is likewise designedunitarily with the respective ring or the housing.

Particularly preferably, the turbine is additionally designed in such amanner that the line of flux of the axial preload through the guideapparatus substantially runs parallel to the rotational axis of theturbine rotor. It is thus provided that the line of flux of the axialpreload substantially runs axially or axially through the guideapparatus. In the case of large spring forces and under unfavourabletransient conditions during which for example the axial spring elementon the one hand is still cold and brings about a great axial force orpreload and on the other hand the guide vane cover ring is alreadyheated and can no longer tolerate high stresses, the guide vane bearingring and/or the guide vane cover ring can be deformed particularlydish-like through the force of the axial spring element if the line offlux through the guide vane bearing ring and/or through the guide vanecover ring substantially runs radially or in radial direction. Throughthe substantially axial course of the line of flux the occurrence ofmoments in the guide apparatus resulting in deformations is prevented.As a consequence, greater axial spring forces can be tolerated,deformations particularly under transient conditions are smaller so thatthe play of the guide vanes can be selected smaller, as a result ofwhich the efficiency of the turbine is improved and the lifespanincreased. More favourable materials can also be used.

Practically, at least one axial spring contact region of the guideapparatus is substantially located on the same radius as the axialspacer or, for example if a plurality of axial spacers and/or axialspring elements or axial spring contact regions are provided, as theaxial spacers. This guarantees a substantially axial line of flux of theaxial preload from the axial spring element through the guide apparatusvia the axial spacers. The axial spring contact region in this case isobviously arranged on the side of the guide vane bearing ring or theguide vane cover ring facing away from the axial spacer, depending onwhich side the of the guide apparatus the axial spring element orelements is/are provided/arranged.

Advantageously, the axial spring contact region is arranged aligned withthe axial spacer. If a plurality of axial spring elements and aplurality of spacers are provided, the corresponding axial contactregions are each arranged or orientated aligned with an axial spacer.The axial spring contact region or the axial spring contact regions arethus arranged in the imagined extension of the axial spacer or spacers.Because of this, it is prevented that moments occur in circumferentialdirection which can likewise result in deformation of the guide vanecover ring and/or the guide van bearing ring. If, therefore, the axialforce introduction point from the axial spring element and the forcetransmission point to the axial spacer are approximately at the sameheight, no undesirable stresses and deformations occur.

Advantageously, at least one axial contact region of the housing issubstantially located on the same radius as the axial spacer and/or asthe axial contact region of the guide apparatus. The guide apparatus ofthe contact region in this case obviously means the region of thehousing which the guide apparatus with the guide vane cover ring or, ifapplicable, with the guide vane bearing ring contacts axially. Thus theaxial guide apparatus contact region is formed for example through oneof the axial depressions described above in which the guide apparatuslies. Wherein, if the guide apparatus with the guide vane cover ringcontacts the axial contact region with the entire area of the guide vanecover ring, the line of flux through the guide apparatus already runssubstantially axially because of the arrangement of the axial spacer/theaxial spacers and of the axial spring contact region/the spring contactregions. If, however, in the housing advantageously one or a pluralityof clearances or recesses open at the edge towards the guide vane coverring are provided through which the medium driving the turbine rotor canflow for heating the guide vane cover ring on both sides, the guide vanecover ring only partially contacts the housing, wherein the axialcontact region of the housing, as described above, is then practicallyarranged substantially on the same radius as the axial spacer or axialspacers. If a plurality of clearances or recesses are arrangeddistributed equiangularly over the circumference of the guide vane coverring or the axial contact region of the housing, the axial (part)contact regions located in between are preferably arranged aligned withthe spacers so that in this case moments in circumferential directionresulting in deformations are also prevented. Obviously, the axialcontact region and/or the axial spring contact region can each be alsodesigned as contact point or line.

Finally, it is provided that the line of flux of the axial preload doesnot deviate by more than 20% from the radius on which the spacer orspacers are located. Because of this a line of flux flow range isdefined, within which the line of flux substantially runs axially or isaxial. Through corresponding arrangement of the axial spring element orthe axial spring contact region, of the axial spacer/or the axialcontact region of the housing, as described above, this preferred lineof flux flow range can be achieved.

The exhaust gas turbocharger according to the invention is characterisedby a turbine as has been described above.

BRIEF DESCRIPTION OF THE DRAWINGS

In the following the invention is explained in more detail by means ofseveral drawings. Here it shows

FIG. 1 An exemplary embodiment of a turbine with a guide apparatus thatis axially and radially moveable without preload,

FIG. 2 A turbine with an axial spring element between the guideapparatus and a turbine housing,

FIG. 3 The turbine with the axial spring element between the guideapparatus and a bearing housing,

FIG. 4 A further exemplary embodiment of the turbine with pinconnections,

FIG. 5 A further exemplary embodiment of the turbine with axial spacers,

FIG. 6 The turbine from FIG. 5 with a pin connection,

FIG. 7 A further exemplary embodiment of the turbine with a radialspring element,

FIG. 8 An enlarged detail of the turbine from FIG. 7,

FIG. 9 The turbine of FIG. 7 with an alternative radial spring element,

FIG. 10 A further exemplary embodiment of the turbine with a pinconnections,

FIG. 11 A further exemplary embodiment of the turbine with pinconnections,

FIG. 12 A further exemplary embodiment of the turbine with pinconnections,

FIG. 13 An exemplary embodiment of the turbine with a radial-axialspring element,

FIG. 14 A further exemplary embodiment of the turbine with an axialspring element and a radial spring element,

FIG. 15 The turbine with an alternative radial-axial spring element,

FIG. 16 A further exemplary embodiment of the turbine with two axialspring elements on a side of the guide apparatus,

FIG. 17 A further exemplary embodiment of the turbine with a coil springas axial spring element,

FIG. 18 A further exemplary embodiment of the turbine with recesses and,

FIG. 19 A preferred line of flux flow through the guide apparatus.

EMBODIMENTS OF THE INVENTION

FIG. 1 shows a turbine 1 of an exhaust gas turbocharger for a motorvehicle which is not shown in more detail here in a schematic sectionalrepresentation. The turbine 1 comprises a turbine rotor 4 rotatablymounted about a rotational axis 3 in a housing 2, wherein only the partabove the rotational axis 3 is shown. The housing 2 of the turbine 1 isdesigned in two parts, wherein one part forms a turbine housing 5 andthe other part a bearing housing 6, wherein the bearing housing 6—withrespect to the rotational axis 3—axially follows the turbine housing 5,and between the turbine housing 5 and the bearing housing 6 a flow crosssection for a medium driving the turbine rotor is formed. The medium, inthe present exemplary embodiment the exhaust gas of the combustionengine, can radially flow into the housing 2 to the turbine rotor 4 andonce it has performed work on the turbine rotor 4, again axially existsfrom the turbine housing 5 as indicated by the arrows 42.

In the housing 2 of the turbine 1 a guide apparatus 7, which has avariable turbine geometry and forms a radial inlet channel 9 for themedium in the flow-through cross section between the turbine housing 5and the bearing housing 6, is additionally mounted. The guide apparatus7 comprises a guide vane bearing ring 10, which coaxially to therotational axis 3 lies in an axial depression 11 of the bearing housing6. On the guide vane bearing ring 10 a plurality of guide vanes 8—ofwhich only one is shown here—are equiangularly arranged distributed overthe guide vane bearing ring 10, so that they surround or frame theturbine rotor 4. The guide apparatus 7 additionally comprises a guidevane cover ring 12 which is orientated coaxially to the rotational axis3 and lies in an axial depression 13 of the turbine housing 5. The guidevane bearing ring 10 and the guide vane cover ring 12 thereby axiallydelimit the inlet channel 9 for the medium driving the turbine rotor 4.The axial spacing of the guide vane bearing ring 10 from the guide vanecover ring herein corresponds substantially to the width of the guidevanes 8. By adjusting the vane angle of the guide vanes the flow-throughcross section in the inlet channel can thus be adjusted or influenced inoperation. By means of this, the power of the turbine 1 can for examplebe adapted to different operating conditions/operating points. Foradjusting, the guide vanes 8 each have a lever arm 14. Advantageously,for actuating or adjusting the vane angle of the guide vanes 8, anadjusting ring which is not shown in more detail here is provided, whichis arranged on the side of the guide vane bearing ring 10 locatedopposite the inlet channel 9 and operationally connected with the leverarms 14 so that by twisting the adjusting ring all guide vanes 8 can besimultaneously adjusted with respect to their vane angle.

In the exemplary embodiment of FIG. 1 the guide apparatus 7 is mountedaxially and radially moveably without preload for material relaxation.To this end, axial play is provided between the guide vane bearing ring10 and the bearing housing 6 and/or between the guide vane cover ring 12and the turbine housing 5, which allows expansion of the components ofthe guide apparatus 7 because of the high temperature of the exhaust gaswithout the guide apparatus 7 or it components (guide vane bearing,guide vanes, guide vane cover ring) having to be clamped in the housing2 in such a manner that stresses develop in the components and/or theindividual components are deformed. In operation, the guide apparatus 7can thus expand axially for example as a result of which material stressis reduced/prevented or material relaxation is guaranteed. Materialrelaxation here substantially means the prevention of the occurrence ofstresses in the material of the components of the guide apparatus 7 suchas for example the material of the guide van bearing ring pin or of theguide vane cover ring 12. The radial moveability of the guide apparatus7 or its components or parts is guaranteed through a suitably wideformation of the axial depressions 11 and 13, so that the guide vanebearing ring 10 in the bearing housing 6 is arranged radially spacedfrom the bearing housing 6 and the guide vane cover ring 12 is arrangedradially spaced from the turbine housing 5. Thus the guide apparatus 7or its components can radially grow unimpeded, so that no stresses aregenerated. In the present exemplary embodiment the components of theguide apparatus 7 loosely contact the housing 2 or one another. In otherwords, the guide apparatus 7 is mounted in the housing 2 of the turbine1 in a floating manner. This mounting of the guide apparatus 7 allowsrelative movement between the guide apparatus 7 and the housing 2 oramong the components the guide apparatus 7, as a result of whichstresses in the components are reduced and the lifespan of the turbine 1is increased. This makes it possible that a particularly small play canbe selected between the guide vanes 8 and the guide vane cover ring 12.In that the guide apparatus 7 or its components are mounted axiallymoveably it is prevented that the guide vanes 8 also “jam” between theguide van bearing ring 10 and the guide vane cover ring 12 under hightemperature loading. The friction between the guide vanes 8 and theguide vane cover ring 12 is likewise reduced when adjusting the vaneangle of the guide vanes 8. Because of this it is additionally preventedthat rapid corrosion/rapid wear of the guide vane cover ring 12 or theguide vanes 8 takes place. Because of the floating mounting or becauseof the absence of screws and/or threaded bores this concept isparticularly favourable in production and can be easily assembled. Theguide apparatus 7 in this case can be provided and installed in theturbine 1 as a preassembled assembly. Alternatively the components ofthe guide apparatus 7 can be inserted individually.

In order to secure a minimum axial spacing between the guide vanebearing ring 10 and the guide vane cover ring 12, axial spacers 15 areprovided between the guide vane bearing 10 and the guide vane cover ring12. These are advantageously arranged distributed equiangularly, whileobviously uneven distribution is also conceivable. The axial spacers 15can be optionally arranged or fixed on the guide vane bearing ring 10,on the guide vane cover ring 12 or alternately on the guide vane bearingring 10 and the guide vane cover ring 12. Particularly preferably theaxial spacers 15 are designed unitarily with the guide vane bearing ring10 or the guide vane cover ring 12.

The turbine rotor 4 is arranged on a shaft 16 which leads into thebearing housing 6 where it is suitably mounted rotatably for example bymeans of rolling bearings and/or slide bearings. On the end of the shaft16 located opposite the turbine rotor 4 a compressor rotor of acompressor of the exhaust gas turbocharger is suitably arranged on theshaft 16 in a rotationally fixed manner. To prevent that hot exhaust gasflows into the bearing housing 6, a sealing element 17 is additionallyarranged between the shaft 16 and the bearing housing 6.

FIG. 2 shows a further exemplary embodiment of the turbine 1 known fromFIG. 1, wherein elements known from FIG. 1 are provided with the samereference characters and are not explained again. This applies also tothe following FIGS. 3 to 17, in which already known elements areprovided with already used reference characters. FIG. 2 shows theturbine 1 in a further simplified representation, wherein the guideapparatus 7 in a simplified manner is merely shown as a box 17. Incontrast with the preceding exemplary embodiment the guide apparatus inFIG. 2 is subjected to axial preload. This is generated by an axialspring element 18 which is arranged between the guide apparatus 7 or theguide vane cover ring 12 which is not shown here and the turbine housing5. The axial spring element 18 thus presses the guide apparatus 7against the bearing housing 6. Thus the guide apparatus 7 contacts thebearing housing 6 as a result of which heat can be effectively andefficiently discharged to the bearing housing 6, so that the guideapparatus 7 is cooled by the bearing housing 6. Through the axialpreload the individual components of the guide apparatus 7 are alsopressed against one another. Thus the axial spring element loads theguide vane cover ring 12, which in turn presses onto the guide vanes 8or, if, present, onto the axial spacers 15 which determine the guidevane play and thus onto the guide vane bearing ring 10. The spring forceof the axial spring element 18 is advantageously selected so small thattemperature-related deformations of the guide apparatus 7 or itscomponents do not result in (jamming) stresses in the components or inthe guide apparatus 7. The guide apparatus 7 and particularly itscomponents are thus mounted sufficiently moveable axially for materialrelaxation.

FIG. 3 shows a further exemplary embodiment of the turbine 1 whichdiffers only slightly from the preceding exemplary embodiment from FIG.2. The substantial difference lies in that the axial spring element 18is arranged between the guide apparatus 7 and the bearing housing 6,wherein in the following exemplary embodiment the axial spring element18 is designed as coil spring 19. The coil spring 19 lies in a springreception 20 of the bearing housing 6, which for example can be formedas a bore or as circumferential groove. The coil spring could likewisebe guided or orientated and positioned by means of a spigot.Alternatively, the axial spring element 18 can also be designed ashelical spring, sponge-like fabric, elastomer element or similar. Thearrangement of the axial spring element 18 between the bearing housing 6and the guide apparatus 7 has the advantage that the spring is locatedon the cool side of the turbine 1. Because of this, the axial springelement 18 is not heated so severely but cooled through the contact withthe cool bearing housing 6.

FIG. 4 shows a further exemplary embodiment of the turbine 1 in adetailed sectional representation, wherein the turbine rotor 4 as wellas the shaft 16 are not shown. The turbine 1 of FIG. 4 substantiallycorresponds to the turbine 1 from FIG. 3, wherein the axial springelement 18 is designed as a disc spring 21. In addition to this, theturbine 1 has two pin connections 22 and 23. The pin connection 22consists of a pin 24 which is orientated axially—that is parallel to therotational axis 3—and lies in a pin reception 25 in the turbine housing5 and engages in a pin reception 26 of the guide vane cover ring 12. Thepin reception 26 in the guide vane cover ring 12 in this case isdesigned as elongated hole 27 which is radially orientated in itslongitudinal extension. The pin connection 23 likewise comprises a pin24 which lies in a pin reception 25 of the turbine housing 5 and engagesin a pin reception 26 of the guide vane cover ring 12. By designing thepin reception 26 of the pin connection 22 as elongated hole 27 the guidevane cover ring 12 can grow radially without obstruction so that no(jamming) stresses can develop in the guide vane cover ring 12 due tohigh temperature.

FIG. 5 shows the turbine 1 of FIG. 4 with the distinction that the pin24 of the pin connection 23 is formed by an axial spacer 15. To thisend, the axial spacer 15 is designed in such a manner that it reachesthrough the guide van cover ring 12 and engages in the pin reception 25of the turbine housing 5.

FIG. 6 shows an enlarged region of the turbine 1. Here, a pin connection29 with a pin 24 is provided between the turbine housing 5 and the guidevane cover ring 12, wherein in contrast with the preceding exemplaryembodiments the pin 24 is orientated radially or perpendicularly to therotational axis 3 or the turbine rotor 4. On the whole, the pinconnections substantially serve as anti-rotation safety of the guideapparatus 7 and allow radial and axial movement of the guide apparatus7. To this end, the pin reception 25 is formed in the turbine housing 5with open edge as elongated hole 30 which in its longitudinal extensionis orientated axially or parallel to the rotational axis 3 of theturbine rotor 4. Here it must be mentioned that with all exemplaryembodiments shown in the figures there is radial and axial moveabilityof the guide apparatus and its components.

FIG. 7 shows a further exemplary embodiment of the turbine 1 in asectional representation, wherein the axial spacers 15 are arranged orfixed on the guide vane bearing ring 10. To this end, the axial spacers15 are each inserted in a corresponding opening formed in the guide vanebearing ring 10. While in the preceding exemplary embodiments of FIGS. 2to 6 the guide apparatus 7 is loaded with an axial preload, the guidevane cover ring 12 in the present exemplary embodiment is additionallyloaded with a radial preload. This is guaranteed by means of a radialspring element 31 which is designed as wavy ring 32 and clamped betweenthe inner radius of the guide vane cover ring 12 and the turbine housing5. The wavy ring 32 positions the guide vane cover ring 12 radially inthe turbine housing 5 and thereby allows radial expansion of the guidevane cover ring 12 so that no temperature-related stresses develop inthe guide vane cover ring.

FIG. 8 shows the wavy ring 32 in an enlarged representation of a detailof FIG. 7. Through the wavy shape of the wavy ring 32 the spring forceof the radial spring element 31 is ensured. The wavy ring 32additionally comprises an arched cross section.

FIG. 9 shows an alternative design of the wavy ring 32, which incontrast with the preceding wavy ring 32 from FIG. 8 has a straightcross section.

FIG. 10 shows a further exemplary embodiment of the turbine 1, whereinin this case the pin connection 29 from FIG. 6 is not arranged betweenthe turbine housing 5 and the guide vane cover ring 12, but between theturbine housing 5 and the guide vane bearing ring 10.

FIG. 11 shows an exemplary embodiment of the turbine 1 whichsubstantially corresponds to the exemplary embodiment of FIG. 4, whereinhere the pin connections 22 and 23 are provided between the bearinghousing 6 and the guide vane bearing ring 10, while the radiallyorientated elongated hole 27 is formed in the face end of the guide vanebearing ring 10 facing away from the inlet channel. The pins 24 of thepin connections 22 and 23 in this case are orientated axially orparallel to the rotational axis 3.

FIG. 12 shows a combination of the pin connections 29 and 23, whereinthe pin connection 29 is formed or provided between the turbine housing5 and the guide vane cover ring 12 and the pin connection 23 between thebearing housing 6 and the guide vane bearing ring 10.

FIG. 13 shows an exemplary embodiments of the turbine 1 with aradial-axial spring element 33, which is arranged between the guide vanebearing ring 10 and the bearing housing 6. The radial-axial springelement 33 is designed as a pleated spring ring 34 with radial pleats,which contacts the bearing housing 6 and the guide vane bearing ring 10both axially as well as radially. Because of this the guide apparatus 7or the guide vane bearing ring 10 is loaded with a preload both axiallyas well as radially.

FIG. 14 likewise shows an exemplary embodiments for simultaneouslyradial and axial preloading of the guide apparatus 7, wherein for theaxial preloading the already know axial spring element 18 and for theradial preloading the radial spring element 31 are provided, which inthis case is designed as L-shaped ring spring element 35 which with aleg areally loads/fixes the guide vane bearing ring 10 radially.

FIG. 15 shows an alternative embodiment of the radial-axial springelement 33 from FIG. 13, which is substantially formed L-shaped and inits leg radially loading the guide vane bearing ring 10 comprises anaxial spring pleat 36 which serves for generating the axial preload. Aheat shield 37, which can be omitted as an option, is axially connectedbetween the radial-axial spring element 33 and the guide vane bearingring 10.

FIG. 16 shows a further exemplary embodiment for generating an axialpreload, wherein in this case two disc springs 21 are provided which areboth in contact between the bearing housing 6 and the guide vane bearingring 10.

FIG. 17 shows an alternative embodiment of the axial spring element 18.Here, the axial spring element 18 is designed as a coil spring 39 whichlies in axial spring receptions 40 which are formed in the bearinghousing 6 and in the guide vane bearing ring 10. It is also conceivableto provide a coil spring 39 which has a conical longitudinal extensionor longitudinal section, for example with wide support surface in thebearing housing 6 and with small support surface in the guide vanebearing ring 10. Obviously the use of other known spring types such asfor example elastomer element, sponge-like fabrics and similar resilientelements is likewise possible. An undercut 41, which in the turbinehousing 5 is formed with open edge to the guide vane cover ring 12, isfluidically connected with an inlet channel 9, so that a part of the hotexhaust gas can enter the undercut 41 and thus also heats the guide vanecover ring 12 from “behind”. Through its wavy shape the wavy ring 32 inthis case secures the fluidic connection in that it positions the guidevane cover ring 12 radially spaced from the turbine housing 5. The guidevane cover ring 12 is thus subjected to the temperature of the medium orthe exhaust gas on both sides, as a result of which uneven deformationof the guide vane cover ring 12 is prevented and thus the play betweenthe guide vanes 8 and the guide vane cover ring 12 can be selectedsmaller. All mentioned spring elements can be designed closed orsegmented.

FIG. 18 shows a further exemplary embodiment of the turbine 1 in asimplified representation. In this exemplary embodiment an axial preloadis generated by means of the axial spring element 18, as for examplealso shown in FIG. 4. Likewise shown is the undercut 41, which can besubjected to an inflow downstream of the guide vanes 8 as indicated byan arrow 43. Furthermore, a second undercut 44 is provided which isformed/arranged radially spaced from the undercut 41, and which can besubjected to inflow downstream of the guide vanes 8, as indicated by anarrow 45. Between the undercuts 41 and 44 there remains a support region46 in which the guide vane cover ring 12 is in contact. Between theguide vane cover ring 12 and the support region 46 a seal 47 isadvantageously arranged which prevents that medium flow past the guideapparatus 7.

In principle, the embodiments described above can be combined with oneanother in any way, for example both the guide vane cover ring as wellas the guide vane bearing ring are pinned or positioned/held by means ofpin connections.

In addition it is possible to arrange/fix at least one axial spacer withpins or pin-like designs of the axial spacer in the guide vane bearingring and/or in the guide vane cover ring.

FIG. 19 substantially corresponds to FIG. 18, so that in the followingmerely the differences are explained. FIG. 19 shows a preferredembodiment of the turbine 1, where the line of flux of the axialpreload, shown as a line 48 in FIG. 19, substantially runs parallel tothe rotational axis 3 of the turbine rotor 4. To this end, the axialspring element is arranged in such a manner that it contacts the guideapparatus 7 or the guide vane bearing ring 10 in an axial spring contactregion 52 which substantially lies on the same radius as the axialspacer 15. In the present exemplary embodiment the substantiallycircle-cylindrical axial spacer 15 with its longitudinal axis or itsrotational axis lies on the radius r_m (pitch circle radius) to therotational axis 3, as shown by an interrupted line 49. Similar appliesto the further axial spacers arranged distributed over the circumferencewhich are not shown here. Because of this, the line of flux (line 48)from the axial spring element 18 is substantially directed axially orparallel to the rotational axis 3 of the turbine rotor 4 through theguide vane bearing ring 10 onto the axial spacer 15. The support region46, which forms an axial contact region 53 of the housing 2 for theguide apparatus 7 is likewise arranged substantially at the same heightor on the same radius as the axial spacer 15, so that the line of flux(line 48) continues to run from the axial spacer 15 via the guide vanecover ring 12 substantially axially or parallel to the rotational axis 3of the turbine rotor 4 into the housing 2.

On the whole, the line of flux (line 48) thus runs substantially axiallyor parallel to the rotational axis 3 through the guide apparatus 7. Thishas the advantage that the elements of the guide apparatus 7,particularly the guide vane cover ring 12 and the guide vane bearingring 10, particularly in the case of unfavourable transient conditions,are not deformed.

If advantageously instead of the disc spring 21 or a plurality of axialspring elements 18, such as for example the coil springs 39, areprovided, these are arranged and orientated aligned with the spacers 15,that is in the imagined extension of the spacers 15. Because of this,stresses and deformations in circumferential direction in the guide vanebearing ring are avoided.

Furthermore, two radii r_i and r_a are shown in FIG. 19 by means ofinterrupted lines 50 and 51 respectively, wherein the radius r_a islarger and the radius r_i is smaller than the radius r_m of the spacers15. The radii r_i and r_a define a line of flux flow range,characterized by a double arrow 54, within which the line of flux (line48) is to run. Practically, the line of flux and the (pitch circle)radii (to the rotational axis 3), on which the different elements (axialspacer 15, axial spring element 18 and axial spring contact region 52and support region 46 or axial contact region 53) or the respectivecontact regions are each arranged between the elements, each onlydeviate by 20% from the radius r_m in both directions.

Instead of the disc spring 21, as shown in FIG. 18, the heat shield 37known from FIG. 15 is provided in FIG. 19, which is of a disc springdesign, while its spring force is substantially smaller than that of thedisc spring 21 and merely serves for sealing.

1. An exhaust gas turbocharger, comprising: a turbine rotor rotatablymounted in a housing, which is associated with at least one guideapparatus forming a radial inlet channel, wherein the turbine rotordrives a medium in the channel, wherein the guide apparatus comprises atleast one of a guide vane bearing ring, a plurality of guide vanesradially surrounding the turbine rotor and located in the inlet channeland a guide vane cover ring, wherein the inlet channel is axiallydelimited by the guide vane bearing ring and the guide vane cover ringwherein the guide vane bearing ring and the guide vane cover ring aremounted at least one of axially and radially moveably relative to eachother and to the housing for material relaxation, and wherein the guideapparatus is subjected to at least one of an axial and radial preload,and wherein a line of flux of the axial preload runs through the guideapparatus substantially parallel to the rotational axis of the turbinerotor.
 2. The turbine according to claim 1, wherein the guide vanebearing ring and the guide vane cover ring each lie in an axialdepression of the housing.
 3. The turbine according to claim 1, whereinthe housing is designed in multiple parts.
 4. The turbine according toclaim 1, wherein a first housing part is a turbine housing.
 5. Theturbine according to claim 1, wherein a second housing part is a bearinghousing.
 6. The turbine according to claim 2, wherein the axialdepression for the guide vane bearing ring is formed in the bearinghousing and the axial depression for the guide vane cover ring is formedin the turbine housing.
 7. The turbine according to claim 1, furthercomprising: at least one axial spring element for generating the axialpreload.
 8. The turbine according to claim 7, wherein the axial springelement is axially arranged between at least one of the guide vanebearing ring and the housing, and the guide vane cover ring and thehousing.
 9. The turbine according to claim 7 wherein the axial springelement is at least one of a helical spring, a coil spring, a discspring, an O-ring and a C-ring.
 10. The turbine according to claim 1,further comprising: at least one radial spring element for generatingthe radial preload.
 11. The turbine according to claim 10, wherein theradial spring element is a wavy ring.
 12. The turbine according to claim1, further comprising: at least one radial-axial spring element forgenerating at least one of the axial and radial preloads.
 13. Theturbine according to claim 1, wherein at least one axial spacer isprovided between the guide vane bearing ring and the guide vane coverring.
 14. The turbine according to claim 13, wherein the axial spacer isarranged on at least one of the guide vane bearing ring and the guidevane cover ring.
 15. The turbine according to claim 13 wherein the axialspacer is designed unitarily with at least one of the guide vane bearingring and the guide vane cover ring.
 16. The turbine according to claim1, wherein at least one of the guide apparatus, the guide vane bearingring and the guide vane cover ring comprise at least one pin connectionfor at least one of aligning and positioning on the housing.
 17. Theturbine according to claim 16, wherein the pin connection comprises atleast one pin, which is inserted in a pin reception of the guideapparatus and the housing.
 18. The turbine according to claim 17,wherein at least one pin reception is designed as elongated hole. 19.The turbine according to claim 18, wherein the elongated hole in itslongitudinal extension is orientated radially or axially.
 20. Theturbine according to claim 17 wherein the pin is orientated axially orradially.
 21. The turbine according to claim 17 wherein at least one pinis formed by one of the axial spacers.
 22. The turbine according toclaim 13 wherein at least one axial spring contact region of the guideapparatus substantially lies on the same radius as the axial spacer. 23.The turbine according to claim 22, wherein the axial spring contactregion is arranged aligned with the axial spacer.
 24. The turbineaccording to claim 22, wherein at least one axial contact region of thehousing for the guide apparatus lies substantially on the same radius asat least one of the axial spacer, the axial spring contact region of theguide apparatus and aligned thereto.
 25. The turbine according to claim22 wherein the line of flux of the axial preload does not deviate bymore than 20% from the radius (r_m), on which the axial spacer lies, inboth directions.
 26. An exhaust gas turbocharger, comprising: at leastone compressor operationally connected mechanically to at least oneturbine rotor, wherein the turbine rotor is rotatable mounted in ahousing, which is associated with at least one guide apparatus forming aradial inlet channel, wherein the guide apparatus includes at least oneof a guide vane bearing ring, a plurality of guide vanes radiallysurrounding the turbine rotor and located in the inlet channel and aguide vane cover ring, wherein the inlet channel is axially delimited bythe guide vane bearing ring and the guide vane cover ring wherein theguide vane bearing ring and the guide vane cover ring are moveablymounted at least one of axially and radially relative to each other andto the housing, and wherein the guide apparatus is subjected to at leastone of an axial and radial preload, and wherein a line of axial preloadflux runs through the guide apparatus substantially parallel to therotational axis of the turbine rotor.